@techreport{oai:jaxa.repo.nii.ac.jp:00041221,
 author = {石田, 洋治 and 野口, 正芳 and 佐藤, 衛 and 神田, 宏 and Ishida, Yoji and Noguchi, Masayoshi and Sato, Mamoru and Kanda, Hiroshi},
 month = {Jul},
 note = {ハイブリッド層流制御(HLFC)は実用上最も有望な航空機抵抗低減技術であるが、これまで理論、実験の両面から系統的に行われた研究は極めて少ない。我々は高亜音速、高レイノルズ数に於けるHLFC翼の空力特性を理論的、実験的に研究しているが、本報告では研究の出発点として、多孔、多溝各吸い込み表面を備えた2次元HLFC翼の、吸い込み有りと無しの場合の抵抗特性の風洞試験結果と、風洞試験において観察された自由流れや模型表面の粗さの影響を考慮に入れた新しい遷移点判定法と境界層計算とを組合わせた数値計算法による実験データの数値解析の結果について報告する。我々のHLFC翼は、実機飛行条件に近いマッハ数およびレイノルズ数条件において、20%を超える全抵抗(ウエーク抵抗と等価吸い込み抵抗の和)の低減を実現出来た。また数値解析は全般的に満足すべき予測を与えた。, Hybrid Laminar Flow Control (HLFC) is one of the most promising aircraft drag reduction technologies. However, very few experimental and theoretical studies have been reported. The aerodynamic characteristics of an HLFC airfoil and wing at high subsonic, high Reynolds number conditions have been investigated both numerically and experimentally. This paper reports the results of the wind tunnel test on drag characteristics, with and without suction, of two-dimensional HLFC airfoils with porous and slot suction approach under some adverse factors against laminar flow, and a numerical analysis of the wind tunnel data, which is based on the boundary layer calculation with a new transition prediction method allowed for the adverse factors and the Squire-Young drag formula. The HLFC models achieved total drag reduction of as high as 20 percent at realistic flight condition and the numerical method has given satisfactory predictions., 資料番号: AA0004252000, レポート番号: NAL TR-1244T},
 title = {Numerical and experimental study of drag characteristics of two-dimensional HLFC airfoils in high subsonic, high Reynolds number flow},
 year = {1994}
}